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This standardization handbook has been developed and is being maintained as a joint effort of the Department of Defense and the Federal Aviation Administration. It provides guidelines and material properties for organic polymer and metal matrix composite materials. It provides a standard source of statistically-based mechanical property data for cu

Thermal properties Electrical properties Joint thermal-mechanical properties lndex of properties by joint and composite system Bearing strength This section describes how the data are presented and organized in this volume (MIL-HDBK-17-2). 1.4.1 Properties and definitions The properties and their definitions are found in the appropriate chapters of Volume 1. Fiber proper- ties and methods for obtaining them are discussed in Chapter 3. Resin properties are presented in Chapter 4. Methods for characterizing prepreg materials are discussed in Chapter 5 and properties and

data set, an asterisk follows the section title. The first set of information in a data section is a summary table containing information on the mate- rials, processing, etc. The box with a heavy border in the upper right-hand corner identifies the first summary table. {Fiber Class)/{Matrix Class) {Nominal FAW) - {Tapeweave Type) Material information is presented for the composite, the prepreg, the fiber, and the matrix. Com- posite material identification is presented as: {Fiber) {Filament-Count)/{Matrix) {TapeNVeave Type) Prepreg identification is included as {Manufacturer) {Commercial Name) {Tapelweave type). For fabric, information such as warp and fill fiber spacing is included when it is available. Fiber identi- fication includes {Manufacturer) {Commercial Name) {Filament-Count) {Sizing) {Twist). Resin

This box contains information which identifies the data set, the type of test for which results are shown, specimen orientation, test conditions, and the classes of data. FAW, fiber areal weight Material identification is provided for the composite material as The range of physical parameters, resin content, fiber volume, ply thickness, composite density, and void content are presented for the data on this particular page.

1.5.1 Materials system codes The materials systems codes which are used in the handbook consist of a fiber system code and a matrix material code separated by a virgule bles 1.5.1 (a) and (b). TABLE 15 .1( a) Fiber system codes. TABLE 1.5.

Two or more adjacent laminae with the same orientation are indicated by adding a subscript, to the angle of the first such lamina, equal to the number of repetitions of laminae with that orienta- tion. Laminae are listed in order from the first laid up to the last. Brackets are used to indicate the be- ginning and the end of the code.

Discussion: For filament winding, a lamina is a layer. Laminae -- Plural of lamina. Laminate -- for fiber-reinforced composites, a consolidated collection of laminae (plies) with one or more orientations with respect to some reference direction. Laminate Orientation -- The configuration of a crossplied composite laminate with regard to the an-

where = initial distance from the neutral axis to the extreme fiber where failure occurs, Modulus of Rupture, in Torsion -- The maximum shear stress in the extreme fiber of a member of circular cross section loaded to failure in torsion calculated from the equation: where = maximum twisting moment,

even. If the population is symmetric about its mean, the sample median is also an estimator of the popu- lation mean. (See Volume 1, Section 8.1.4.) Sample Standard Deviation -- The square root of the sample variance. (See Volume 1, Section 8.1.4.) Sample Variance -- The sum of the squared deviations from the sample mean, divided by n-l. (See

Maximum Short Term Service Temperature: 220°F (dry), 16 0°F (wet) Typical applications: Primary and secondary structural applications where improved fatigue and excel- lent mechanical strength is important such as helicopters and general aviation.

The laminate properties presented in this chapter have been generated in test programs conducted at U.S. Forest Products Laboratory and elsewhere (Reference A1.2).' Properties are given for fiberglass with epoxy, phenolic, silicone and polyester resins and for boron with epoxy. Additional information on these and other material combinations will be issued as supplements or revisions of the present handbook edition. Objectives The objectives of the handbook test program are to obtain statistically significant data for materials currently in use and to determine the degree of reproducibility attained in their fabrication. A minimum re- quirement is that test results include data from three sets of panels which are representative of the manu- facturing procedures employed by three different fabricators. The properties listed in the charts and tables

This standardization handbook has been developed and is being maintained as a joint effort of the Department of Defense and the Federal Aviation Administration. It provides guidelines and material properties for organic polymer and metal matrix composite materials. It provides a standard source of statistically-based mechanical property data for cu

Thermal properties Electrical properties Joint thermal-mechanical properties lndex of properties by joint and composite system Bearing strength This section describes how the data are presented and organized in this volume (MIL-HDBK-17-2). 1.4.1 Properties and definitions The properties and their definitions are found in the appropriate chapters of Volume 1. Fiber proper- ties and methods for obtaining them are discussed in Chapter 3. Resin properties are presented in Chapter 4. Methods for characterizing prepreg materials are discussed in Chapter 5 and properties and

data set, an asterisk follows the section title. The first set of information in a data section is a summary table containing information on the mate- rials, processing, etc. The box with a heavy border in the upper right-hand corner identifies the first summary table. {Fiber Class)/{Matrix Class) {Nominal FAW) - {Tapeweave Type) Material information is presented for the composite, the prepreg, the fiber, and the matrix. Com- posite material identification is presented as: {Fiber) {Filament-Count)/{Matrix) {TapeNVeave Type) Prepreg identification is included as {Manufacturer) {Commercial Name) {Tapelweave type). For fabric, information such as warp and fill fiber spacing is included when it is available. Fiber identi- fication includes {Manufacturer) {Commercial Name) {Filament-Count) {Sizing) {Twist). Resin

This box contains information which identifies the data set, the type of test for which results are shown, specimen orientation, test conditions, and the classes of data. FAW, fiber areal weight Material identification is provided for the composite material as The range of physical parameters, resin content, fiber volume, ply thickness, composite density, and void content are presented for the data on this particular page.

1.5.1 Materials system codes The materials systems codes which are used in the handbook consist of a fiber system code and a matrix material code separated by a virgule bles 1.5.1 (a) and (b). TABLE 15 .1( a) Fiber system codes. TABLE 1.5.

Two or more adjacent laminae with the same orientation are indicated by adding a subscript, to the angle of the first such lamina, equal to the number of repetitions of laminae with that orienta- tion. Laminae are listed in order from the first laid up to the last. Brackets are used to indicate the be- ginning and the end of the code.

Discussion: For filament winding, a lamina is a layer. Laminae -- Plural of lamina. Laminate -- for fiber-reinforced composites, a consolidated collection of laminae (plies) with one or more orientations with respect to some reference direction. Laminate Orientation -- The configuration of a crossplied composite laminate with regard to the an-

where = initial distance from the neutral axis to the extreme fiber where failure occurs, Modulus of Rupture, in Torsion -- The maximum shear stress in the extreme fiber of a member of circular cross section loaded to failure in torsion calculated from the equation: where = maximum twisting moment,

even. If the population is symmetric about its mean, the sample median is also an estimator of the popu- lation mean. (See Volume 1, Section 8.1.4.) Sample Standard Deviation -- The square root of the sample variance. (See Volume 1, Section 8.1.4.) Sample Variance -- The sum of the squared deviations from the sample mean, divided by n-l. (See

Maximum Short Term Service Temperature: 220°F (dry), 16 0°F (wet) Typical applications: Primary and secondary structural applications where improved fatigue and excel- lent mechanical strength is important such as helicopters and general aviation.

The laminate properties presented in this chapter have been generated in test programs conducted at U.S. Forest Products Laboratory and elsewhere (Reference A1.2).' Properties are given for fiberglass with epoxy, phenolic, silicone and polyester resins and for boron with epoxy. Additional information on these and other material combinations will be issued as supplements or revisions of the present handbook edition. Objectives The objectives of the handbook test program are to obtain statistically significant data for materials currently in use and to determine the degree of reproducibility attained in their fabrication. A minimum re- quirement is that test results include data from three sets of panels which are representative of the manu- facturing procedures employed by three different fabricators. The properties listed in the charts and tables

This standardization handbook has been developed and is being maintained as a joint effort of the Department of Defense and the Federal Aviation Administration. It provides guidelines and material properties for organic polymer and metal matrix composite materials. It provides a standard source of statistically-based mechanical property data for cu

Thermal properties Electrical properties Joint thermal-mechanical properties lndex of properties by joint and composite system Bearing strength This section describes how the data are presented and organized in this volume (MIL-HDBK-17-2). 1.4.1 Properties and definitions The properties and their definitions are found in the appropriate chapters of Volume 1. Fiber proper- ties and methods for obtaining them are discussed in Chapter 3. Resin properties are presented in Chapter 4. Methods for characterizing prepreg materials are discussed in Chapter 5 and properties and

data set, an asterisk follows the section title. The first set of information in a data section is a summary table containing information on the mate- rials, processing, etc. The box with a heavy border in the upper right-hand corner identifies the first summary table. {Fiber Class)/{Matrix Class) {Nominal FAW) - {Tapeweave Type) Material information is presented for the composite, the prepreg, the fiber, and the matrix. Com- posite material identification is presented as: {Fiber) {Filament-Count)/{Matrix) {TapeNVeave Type) Prepreg identification is included as {Manufacturer) {Commercial Name) {Tapelweave type). For fabric, information such as warp and fill fiber spacing is included when it is available. Fiber identi- fication includes {Manufacturer) {Commercial Name) {Filament-Count) {Sizing) {Twist). Resin

This box contains information which identifies the data set, the type of test for which results are shown, specimen orientation, test conditions, and the classes of data. FAW, fiber areal weight Material identification is provided for the composite material as The range of physical parameters, resin content, fiber volume, ply thickness, composite density, and void content are presented for the data on this particular page.

1.5.1 Materials system codes The materials systems codes which are used in the handbook consist of a fiber system code and a matrix material code separated by a virgule bles 1.5.1 (a) and (b). TABLE 15 .1( a) Fiber system codes. TABLE 1.5.

Two or more adjacent laminae with the same orientation are indicated by adding a subscript, to the angle of the first such lamina, equal to the number of repetitions of laminae with that orienta- tion. Laminae are listed in order from the first laid up to the last. Brackets are used to indicate the be- ginning and the end of the code.

Discussion: For filament winding, a lamina is a layer. Laminae -- Plural of lamina. Laminate -- for fiber-reinforced composites, a consolidated collection of laminae (plies) with one or more orientations with respect to some reference direction. Laminate Orientation -- The configuration of a crossplied composite laminate with regard to the an-

where = initial distance from the neutral axis to the extreme fiber where failure occurs, Modulus of Rupture, in Torsion -- The maximum shear stress in the extreme fiber of a member of circular cross section loaded to failure in torsion calculated from the equation: where = maximum twisting moment,

even. If the population is symmetric about its mean, the sample median is also an estimator of the popu- lation mean. (See Volume 1, Section 8.1.4.) Sample Standard Deviation -- The square root of the sample variance. (See Volume 1, Section 8.1.4.) Sample Variance -- The sum of the squared deviations from the sample mean, divided by n-l. (See

Maximum Short Term Service Temperature: 220°F (dry), 16 0°F (wet) Typical applications: Primary and secondary structural applications where improved fatigue and excel- lent mechanical strength is important such as helicopters and general aviation.

The laminate properties presented in this chapter have been generated in test programs conducted at U.S. Forest Products Laboratory and elsewhere (Reference A1.2).' Properties are given for fiberglass with epoxy, phenolic, silicone and polyester resins and for boron with epoxy. Additional information on these and other material combinations will be issued as supplements or revisions of the present handbook edition. Objectives The objectives of the handbook test program are to obtain statistically significant data for materials currently in use and to determine the degree of reproducibility attained in their fabrication. A minimum re- quirement is that test results include data from three sets of panels which are representative of the manu- facturing procedures employed by three different fabricators. The properties listed in the charts and tables

This standardization handbook has been developed and is being maintained as a joint effort of the Department of Defense and the Federal Aviation Administration. It provides guidelines and material properties for organic polymer and metal matrix composite materials. It provides a standard source of statistically-based mechanical property data for cu

Thermal properties Electrical properties Joint thermal-mechanical properties lndex of properties by joint and composite system Bearing strength This section describes how the data are presented and organized in this volume (MIL-HDBK-17-2). 1.4.1 Properties and definitions The properties and their definitions are found in the appropriate chapters of Volume 1. Fiber proper- ties and methods for obtaining them are discussed in Chapter 3. Resin properties are presented in Chapter 4. Methods for characterizing prepreg materials are discussed in Chapter 5 and properties and

data set, an asterisk follows the section title. The first set of information in a data section is a summary table containing information on the mate- rials, processing, etc. The box with a heavy border in the upper right-hand corner identifies the first summary table. {Fiber Class)/{Matrix Class) {Nominal FAW) - {Tapeweave Type) Material information is presented for the composite, the prepreg, the fiber, and the matrix. Com- posite material identification is presented as: {Fiber) {Filament-Count)/{Matrix) {TapeNVeave Type) Prepreg identification is included as {Manufacturer) {Commercial Name) {Tapelweave type). For fabric, information such as warp and fill fiber spacing is included when it is available. Fiber identi- fication includes {Manufacturer) {Commercial Name) {Filament-Count) {Sizing) {Twist). Resin

This box contains information which identifies the data set, the type of test for which results are shown, specimen orientation, test conditions, and the classes of data. FAW, fiber areal weight Material identification is provided for the composite material as The range of physical parameters, resin content, fiber volume, ply thickness, composite density, and void content are presented for the data on this particular page.

1.5.1 Materials system codes The materials systems codes which are used in the handbook consist of a fiber system code and a matrix material code separated by a virgule bles 1.5.1 (a) and (b). TABLE 15 .1( a) Fiber system codes. TABLE 1.5.

Two or more adjacent laminae with the same orientation are indicated by adding a subscript, to the angle of the first such lamina, equal to the number of repetitions of laminae with that orienta- tion. Laminae are listed in order from the first laid up to the last. Brackets are used to indicate the be- ginning and the end of the code.

Discussion: For filament winding, a lamina is a layer. Laminae -- Plural of lamina. Laminate -- for fiber-reinforced composites, a consolidated collection of laminae (plies) with one or more orientations with respect to some reference direction. Laminate Orientation -- The configuration of a crossplied composite laminate with regard to the an-

where = initial distance from the neutral axis to the extreme fiber where failure occurs, Modulus of Rupture, in Torsion -- The maximum shear stress in the extreme fiber of a member of circular cross section loaded to failure in torsion calculated from the equation: where = maximum twisting moment,

even. If the population is symmetric about its mean, the sample median is also an estimator of the popu- lation mean. (See Volume 1, Section 8.1.4.) Sample Standard Deviation -- The square root of the sample variance. (See Volume 1, Section 8.1.4.) Sample Variance -- The sum of the squared deviations from the sample mean, divided by n-l. (See

Maximum Short Term Service Temperature: 220°F (dry), 16 0°F (wet) Typical applications: Primary and secondary structural applications where improved fatigue and excel- lent mechanical strength is important such as helicopters and general aviation.

The laminate properties presented in this chapter have been generated in test programs conducted at U.S. Forest Products Laboratory and elsewhere (Reference A1.2).' Properties are given for fiberglass with epoxy, phenolic, silicone and polyester resins and for boron with epoxy. Additional information on these and other material combinations will be issued as supplements or revisions of the present handbook edition. Objectives The objectives of the handbook test program are to obtain statistically significant data for materials currently in use and to determine the degree of reproducibility attained in their fabrication. A minimum re- quirement is that test results include data from three sets of panels which are representative of the manu- facturing procedures employed by three different fabricators. The properties listed in the charts and tables

This standardization handbook has been developed and is being maintained as a joint effort of the Department of Defense and the Federal Aviation Administration. It provides guidelines and material properties for organic polymer and metal matrix composite materials. It provides a standard source of statistically-based mechanical property data for cu

Thermal properties Electrical properties Joint thermal-mechanical properties lndex of properties by joint and composite system Bearing strength This section describes how the data are presented and organized in this volume (MIL-HDBK-17-2). 1.4.1 Properties and definitions The properties and their definitions are found in the appropriate chapters of Volume 1. Fiber proper- ties and methods for obtaining them are discussed in Chapter 3. Resin properties are presented in Chapter 4. Methods for characterizing prepreg materials are discussed in Chapter 5 and properties and

data set, an asterisk follows the section title. The first set of information in a data section is a summary table containing information on the mate- rials, processing, etc. The box with a heavy border in the upper right-hand corner identifies the first summary table. {Fiber Class)/{Matrix Class) {Nominal FAW) - {Tapeweave Type) Material information is presented for the composite, the prepreg, the fiber, and the matrix. Com- posite material identification is presented as: {Fiber) {Filament-Count)/{Matrix) {TapeNVeave Type) Prepreg identification is included as {Manufacturer) {Commercial Name) {Tapelweave type). For fabric, information such as warp and fill fiber spacing is included when it is available. Fiber identi- fication includes {Manufacturer) {Commercial Name) {Filament-Count) {Sizing) {Twist). Resin

This box contains information which identifies the data set, the type of test for which results are shown, specimen orientation, test conditions, and the classes of data. FAW, fiber areal weight Material identification is provided for the composite material as The range of physical parameters, resin content, fiber volume, ply thickness, composite density, and void content are presented for the data on this particular page.

1.5.1 Materials system codes The materials systems codes which are used in the handbook consist of a fiber system code and a matrix material code separated by a virgule bles 1.5.1 (a) and (b). TABLE 15 .1( a) Fiber system codes. TABLE 1.5.

Two or more adjacent laminae with the same orientation are indicated by adding a subscript, to the angle of the first such lamina, equal to the number of repetitions of laminae with that orienta- tion. Laminae are listed in order from the first laid up to the last. Brackets are used to indicate the be- ginning and the end of the code.

Discussion: For filament winding, a lamina is a layer. Laminae -- Plural of lamina. Laminate -- for fiber-reinforced composites, a consolidated collection of laminae (plies) with one or more orientations with respect to some reference direction. Laminate Orientation -- The configuration of a crossplied composite laminate with regard to the an-

where = initial distance from the neutral axis to the extreme fiber where failure occurs, Modulus of Rupture, in Torsion -- The maximum shear stress in the extreme fiber of a member of circular cross section loaded to failure in torsion calculated from the equation: where = maximum twisting moment,

even. If the population is symmetric about its mean, the sample median is also an estimator of the popu- lation mean. (See Volume 1, Section 8.1.4.) Sample Standard Deviation -- The square root of the sample variance. (See Volume 1, Section 8.1.4.) Sample Variance -- The sum of the squared deviations from the sample mean, divided by n-l. (See

Maximum Short Term Service Temperature: 220°F (dry), 16 0°F (wet) Typical applications: Primary and secondary structural applications where improved fatigue and excel- lent mechanical strength is important such as helicopters and general aviation.

The laminate properties presented in this chapter have been generated in test programs conducted at U.S. Forest Products Laboratory and elsewhere (Reference A1.2).' Properties are given for fiberglass with epoxy, phenolic, silicone and polyester resins and for boron with epoxy. Additional information on these and other material combinations will be issued as supplements or revisions of the present handbook edition. Objectives The objectives of the handbook test program are to obtain statistically significant data for materials currently in use and to determine the degree of reproducibility attained in their fabrication. A minimum re- quirement is that test results include data from three sets of panels which are representative of the manu- facturing procedures employed by three different fabricators. The properties listed in the charts and tables

This standardization handbook has been developed and is being maintained as a joint effort of the Department of Defense and the Federal Aviation Administration. It provides guidelines and material properties for organic polymer and metal matrix composite materials. It provides a standard source of statistically-based mechanical property data for cu

Thermal properties Electrical properties Joint thermal-mechanical properties lndex of properties by joint and composite system Bearing strength This section describes how the data are presented and organized in this volume (MIL-HDBK-17-2). 1.4.1 Properties and definitions The properties and their definitions are found in the appropriate chapters of Volume 1. Fiber proper- ties and methods for obtaining them are discussed in Chapter 3. Resin properties are presented in Chapter 4. Methods for characterizing prepreg materials are discussed in Chapter 5 and properties and

data set, an asterisk follows the section title. The first set of information in a data section is a summary table containing information on the mate- rials, processing, etc. The box with a heavy border in the upper right-hand corner identifies the first summary table. {Fiber Class)/{Matrix Class) {Nominal FAW) - {Tapeweave Type) Material information is presented for the composite, the prepreg, the fiber, and the matrix. Com- posite material identification is presented as: {Fiber) {Filament-Count)/{Matrix) {TapeNVeave Type) Prepreg identification is included as {Manufacturer) {Commercial Name) {Tapelweave type). For fabric, information such as warp and fill fiber spacing is included when it is available. Fiber identi- fication includes {Manufacturer) {Commercial Name) {Filament-Count) {Sizing) {Twist). Resin

This box contains information which identifies the data set, the type of test for which results are shown, specimen orientation, test conditions, and the classes of data. FAW, fiber areal weight Material identification is provided for the composite material as The range of physical parameters, resin content, fiber volume, ply thickness, composite density, and void content are presented for the data on this particular page.

1.5.1 Materials system codes The materials systems codes which are used in the handbook consist of a fiber system code and a matrix material code separated by a virgule bles 1.5.1 (a) and (b). TABLE 15 .1( a) Fiber system codes. TABLE 1.5.

Two or more adjacent laminae with the same orientation are indicated by adding a subscript, to the angle of the first such lamina, equal to the number of repetitions of laminae with that orienta- tion. Laminae are listed in order from the first laid up to the last. Brackets are used to indicate the be- ginning and the end of the code.

Discussion: For filament winding, a lamina is a layer. Laminae -- Plural of lamina. Laminate -- for fiber-reinforced composites, a consolidated collection of laminae (plies) with one or more orientations with respect to some reference direction. Laminate Orientation -- The configuration of a crossplied composite laminate with regard to the an-

where = initial distance from the neutral axis to the extreme fiber where failure occurs, Modulus of Rupture, in Torsion -- The maximum shear stress in the extreme fiber of a member of circular cross section loaded to failure in torsion calculated from the equation: where = maximum twisting moment,

even. If the population is symmetric about its mean, the sample median is also an estimator of the popu- lation mean. (See Volume 1, Section 8.1.4.) Sample Standard Deviation -- The square root of the sample variance. (See Volume 1, Section 8.1.4.) Sample Variance -- The sum of the squared deviations from the sample mean, divided by n-l. (See

Maximum Short Term Service Temperature: 220°F (dry), 16 0°F (wet) Typical applications: Primary and secondary structural applications where improved fatigue and excel- lent mechanical strength is important such as helicopters and general aviation.

The laminate properties presented in this chapter have been generated in test programs conducted at U.S. Forest Products Laboratory and elsewhere (Reference A1.2).' Properties are given for fiberglass with epoxy, phenolic, silicone and polyester resins and for boron with epoxy. Additional information on these and other material combinations will be issued as supplements or revisions of the present handbook edition. Objectives The objectives of the handbook test program are to obtain statistically significant data for materials currently in use and to determine the degree of reproducibility attained in their fabrication. A minimum re- quirement is that test results include data from three sets of panels which are representative of the manu- facturing procedures employed by three different fabricators. The properties listed in the charts and tables